JP2010100283A - Helicopter - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a helicopter designed so as to inexpensively and easily minimize transmission of vibration and noise to a cabin. <P>SOLUTION: The helicopter has: a main rotation wing (3); a body (2); a transmission (7) operatively connected to the main rotation wing (3); a support body (14) for supporting at least the transmission (7); a connection means (20) provided with a first connection member (21); second connection means (31, 32, 33, 34) connected to the support body (14) and the body (2); and an elastic means (41) interposed between the first connection member (21) and the second connection members (31, 32, 33, 34). <P>COPYRIGHT: (C)2010,JPO&INPIT

Description

  The present invention relates to a helicopter.

  Known helicopters include a fuselage that constitutes a forward occupant cabin, and a main rotor mounted at the top of the center of the fuselage to generate the lift and thrust necessary to support and advance the helicopter. The anti-torque rotor (torque balanced rotor) protrudes from the tail fin of the helicopter.

  Specifically, the main rotor has a drive shaft and a number of blades (wings) pivotally connected to the drive shaft via a hub.

  The helicopter also has at least one engine, a transmission (transmission device) provided between the engine and the drive shaft, a support body that supports the drive shaft and the transmission, and a connecting device that connects the fuselage to the support body. is doing. In other words, the fuselage is “suspended” from the support body by the coupling device.

  During normal operation of the helicopter, the engine applies drive torque to the transmission. According to the law of action and reaction, the reaction torque is transmitted to the support body, and then transmitted from the support body to the fuselage by the coupling device, and balanced by the counter-direction torque applied to the fuselage by the tail rotor blades.

  The coupling device inevitably transmits vibrations and noise to the fuselage, and thus to the cabin, thus compromising passenger comfort.

  There is a desire within the industry to minimize the transmission of such vibrations and noise to the cabin, particularly within a predetermined frequency range.

  An object of the present invention is to provide a helicopter designed to achieve at least one of the above-mentioned demands inexpensively and easily.

  According to the present invention, a helicopter according to claim 1 is provided.

1 is a side view of a helicopter according to the present invention. FIG. 2 is an enlarged perspective view of a connecting device constituting a part of the helicopter in FIG. 1. FIG. 3 is an enlarged view in which the coupling device of FIG. 2 is partially disassembled. It is the top view which fractured | ruptured a part of coupling device of FIG.2 and FIG.3. FIG. 5 is a cross-sectional view of a portion of the coupling device of FIGS. 2-4 with parts omitted for clarity. It is a figure which shows one of a series of processes in the assembly of the coupling device of FIGS. It is a figure which shows one of a series of processes in the assembly of the coupling device of FIGS. It is a figure which shows one of a series of processes in the assembly of the coupling device of FIGS.

  The preferred embodiments of the present invention will be described below with reference to the accompanying drawings.

  Reference numeral 1 in FIG. 1 denotes a helicopter, which helicopter 1 includes a fuselage 2 including a nose part 5, at least one engine 6 (shown schematically only in FIG. 1), and lifts and advances the helicopter 1. The main rotor 3 is substantially attached to the uppermost part of the fuselage 2 in order to generate the lift and thrust necessary for the main body 2.

  The main rotor 3 substantially has a drive shaft 10, a hub 11 pivotally connected to the drive shaft 10, and a number of blades pivotally connected to the hub 11. , Extending in respective directions across the axis A of the drive shaft 10.

  The fuselage 2 constitutes a cabin 8 that is normally occupied by an occupant, and the boundary of the cabin 8 is defined by the wall 15 of the fuselage 2 on the side facing the main rotor 3.

  The helicopter 1 also includes a transmission 7 (shown schematically in FIG. 1 only) that operatively couples the output member 13 of the engine 6 to the drive shaft 10, and the output member 13, transmission 7 and drive shaft 10. It has a stator body that is rotatably supported.

  FIG. 1 shows only the box 14 of the stator body, which protrudes from the wall 15 to the opposite side of the cabin 8 and supports the final stage of the transmission 7 and the drive shaft 10 rotatably around the axis A. Yes.

  The helicopter 1 also has a tail anti-torque rotor 4 protruding from the tail fin of the fuselage 2 at the end opposite to the nose part 5 and connecting means 16 for connecting the box 14 to the wall 15 of the fuselage 2. ing.

  The connecting means 16 substantially comprises a number (four in the illustrated example) of rods 17 and a connecting device 20, which are connected to the sides of the box 14 and the respective fastening points to the wall 15. The connecting device 20 is connected to the bottom edge of the box 14 and the wall 15, and transmits reaction torque to the body 2. .

  Specifically, the reaction torque is a torque equal to and opposite to the drive torque transmitted from the engine 6 to the drive shaft 10 via the transmission 7 according to the law of action and reaction. The balance is maintained by the opposite direction torque transmitted to the box 14 and generated by the tail rotor blades 4, that is, the balance is achieved.

  The connecting device 20 substantially includes a cross member 21, two connecting members 25 and 26, two members 31 and 32, and two members 33 and 34 (see FIG. 4). The cross member 21 has a flange 22 bolted to the lowermost edge of the box 14 and two V-shaped additional portions 23, 24, the flange 22 having a circular opening with an axis B, The axis A extends through the opening, and the additional portions 23 and 24 extend so as to taper on both sides of the axis B and protrude from the respective portions of the flange 22. The two connecting members 25 and 26 are respectively arranged on both sides of the axis B, and each connecting member 25 and 26 is perpendicular to the axis B and is between the two plates 29 and the two plates 29 facing each other. Have two side walls 30 interposed perpendicularly thereto. The two members 31 and 32 are connected to the wall 15 of the body 2 and to the side wall 30 of the connecting member 25. The two members 33 and 34 are connected to the wall 15 of the body 2 and to the side wall 30 of the connecting member 26.

  Specifically, the flange 22 has a large number of holes 35 arranged at equal intervals around the axis B, and bolts (not shown) fixed to the lowermost edge of the box 14 are provided in the holes 35. It is fitted.

  Each additional portion 23, 24 extends so as to taper on both sides of the axis B, and has two sides extending symmetrically with respect to the respective axes C, D, and a screw extending along each axis C, D A threaded hole 36 (shown in FIGS. 5 to 8), which is located on the opposite side of the open first axial end located opposite the axis B, is provided. And a closed second axial end.

  Referring to FIGS. 6 and 7, each of the connecting members 25, 26 is disposed in a trapezoidal seat portion 27 with which the respective additional portions 23, 24 are engaged, and on each side of the seat portion 27, and each side wall 30. The two seats 28 having a rectangular column shape and a rectangular cross section whose boundary is determined by Specifically, the rectangular cross-section seat portion 28 of each connecting member 25, 26 communicates with the corresponding trapezoidal seat portion 27.

  The connecting member 25 has a through hole 37 having an axis C, which is aligned axially with the threaded hole 36 of the additional portion 23, and the connecting member 26 has a through hole having an axis D. There is a hole 37, which is aligned axially with the threaded hole 36 of the additional portion 24.

  When the coupling device 20 is assembled, the threaded hole 36 extending along the axis C is engaged with the threaded hole 36 of the additional portion 23 and the through hole 37 of the coupling member 25, and the thread of the additional portion 24 is also engaged. A threaded pin 45 extending along the axis D is engaged with the attachment hole 36 and the through hole 37 of the connecting member 26.

  The axis C and the axis D are inclined with respect to each other, intersect at the center O of the flange 22, and define a plane perpendicular to the axis B.

  With respect to the normal flight axis of the helicopter 1 extending from the tail rotor 4 to the nose 5, the axis C defines an angle β and the axis D defines an angle α. Specifically, the angles β and α are obtuse and equal.

  The axis E substantially coincides with the longitudinal axis of the body 2 and is perpendicular to the axis F shown in FIGS. 3, 4, 6, 7 and 8.

  Each side wall 30 of the connecting member 25 is interposed between the members 31 and 32 and the side portion of the additional portion 23.

  Similarly, each side wall 30 of the connecting member 26 is interposed between the members 33 and 34 and the side portion of the additional portion 24.

  The members 31, 32, 33, 34 are parallel to the main wall 38 that cooperates with the side walls 30 of the connecting members 25, 26, and to protrude from both ends of the main wall 38 on both sides of the connecting members 25, 26. Two side walls 39.

  Each member 31, 32, 33, 34 is fixed to the wall 15 of the body 2 by a respective bolt 19 (not shown) having an axis G parallel to the axis B.

  The coupling device 20 advantageously has elastic means interposed between the members 31, 32 and the additional part 23 and between the members 33, 34 and the additional part 24.

  In particular, the coupling device 20 has four damping assemblies 40 housed in a rectangular section seat 28, each damping assembly 40 comprising a number of layers 41 of elastic material, in particular cured rubber, A large number of metal plates 42 are provided, and the large number of layers 41 and the large number of plates 42 are alternately connected by an adhesive material layer (not shown) (see FIGS. 4 and 5). In the example shown, the layer 41 and the plate 42 are rectangular and lie in a plane parallel to the sidewall 30 including the seat 28.

  The damping assembly 40 is interposed between the side portions of the additional portions 23 and 24 and the members 31, 32, 33, and 34, so that vibration transmission from the cross member 21 to the wall 15 of the body 2 is reduced. The

  Each damping assembly 40 has two plates 43, 44 made of metal, which are connected to the layer 41 closest to the axes C, D by an adhesive material, and the plates 43 are members 31, 32. , 33 and 34 are connected to the layer 41 closest to them.

  The plate 43 of each damping assembly 40 has two protrusions 50 that protrude away from the additional portions 23, 24, and the protrusions 50 are formed on the main walls 38 of the members 31, 32, 33, 34. Engage with the seat portion 51 (see FIGS. 5, 7, and 8).

  The plate 44 of each damping assembly 40 has two protrusions 52 that protrude toward the additional portions 23, 24, which are formed on the sides of the additional portions 23, 24. Engages with the seat 53 (see FIGS. 5, 6, and 7).

  The protrusions 50, 52 of the damping assembly 40 that engage the rectangular section seat 28 of the connecting member 25 are parallel to each other and extend along respective axes that are substantially perpendicular to the side wall 30 of the connecting member 25. ing.

  Similarly, the protrusions 50, 52 of the damping assembly 40 that engage the rectangular cross-section seat 28 of the connecting member 26 are parallel to each other and along respective axes that are substantially perpendicular to the side wall 30 of the connecting member 26. It extends.

  Due to the connection between the projecting portions 50 and 52 and the corresponding seat portions 51 and 53, torque reaction along the axis B is transmitted from the additional portions 23 and 24 to the members 31, 32, 33 and 34.

  The helicopter 1 also has adjusting means 60 for adjusting the preload acting on the layer 41 of the damping assembly 40 (see FIGS. 5-8).

  The adjustment means 60 advantageously has two pairs of pins 61, two pairs of threaded holes 62, and two pairs of through holes 63 for each damping assembly 40 (see FIGS. 5-8). ). The two pairs of pins 61 have parallel threaded ends that extend along respective axes perpendicular to the side walls 30 of the connecting members 25, 26. The two pairs of threaded holes 62 are constituted by the side walls 30 of the connecting members 25, 26, and the respective pairs of threaded pins 61 engage with the two pairs of threaded holes 62. The two pairs of through holes 63 are formed in the main wall 38 of the members 31, 32, 33, 34, and the respective pins 61 pass through the two pairs of through holes 63.

  Specifically, the seat portion 51 of each member 31, 32, 33, 34 is disposed between two pairs of through-holes 63, and the rectangular cross-section seat portion 28 that houses each damping assembly 40 includes two pairs. Located between the threaded holes 62.

  6-8 illustrate the assembly sequence of the pair of damping assemblies 40 of the coupling device 20.

  Specifically, FIGS. 6 to 8 show the assembly order of the damping assembly 40 interposed between the two sides of the additional portion 23 and the members 31 and 32.

  The same applies to the assembly of the damping assembly 40 interposed between the two sides of the additional portion 24 and the members 33, 34 and is therefore not shown in detail.

  Specifically, the additional portion 23 is inserted inside the seat 27 of the connecting member 25 (see FIG. 6), and the threaded pin 45 is passed through the through hole 37 and fastened in the threaded hole 36 ( (See FIG. 7).

  The damping assembly 40 is then inserted inside the rectangular section seat 28 of the connecting member 25, and the members 31, 32 are secured to the side wall 30 of the connecting member 25 by threaded pins 61, whereby each The protrusions 50 and 52 of the damping assembly 40 engage with a seat 51 formed on the member 31 and a seat 53 formed on the side of the additional portion 23, respectively.

  Thus, the damping assembly 40 is gripped at a predetermined position between the members 31, 32 and the side of the additional portion 23 (see FIG. 8).

  At this point, the threaded pin 45 is loosened and removed from the threaded hole 36.

  In actual use, the engine 6 rotates the drive shaft 10 of the main rotor 3.

  The drive shaft 10 rotates the blade 12 via the hub 11 and generates the lift and thrust necessary to lift and advance the helicopter 1.

  Lift and thrust are transmitted to the box 14 and transmitted from the box 14 to the wall 15 of the body 2 mainly via the rod 17.

  The torque transmitted from the drive shaft 10 causes a torque reaction according to the law of action and reaction, and this torque reaction acts on the box 14 in the same direction as the torque acting on the drive shaft 10 and in the opposite direction.

  The torque reaction is transmitted via the connecting device 20 and is transmitted to the wall 15 of the body 2.

  Specifically, the torque reaction is transmitted from the additional parts 23, 24 to the plate 44 of the damping assembly 40 by a pin (protrusion) 52 that engages the seat 53, and from the plate 43 of the damping assembly 40 to the member. 31, 32, 33, 34 is transmitted by a pin (protrusion) 50 that engages the seat 51, and then transmitted to the wall 15 of the body 2 by the members 31, 32, 33, 34.

  The operation of the main rotor 3 causes vibration in the box 14.

  The vibration generated in the box 14 and the noise associated therewith are transmitted from the box 14 to the flange 22 and its additional parts 23, 24.

  Since the damping assembly 40 is provided with a layer 41 of elastic material, it absorbs the vibrations and noises within a predetermined frequency range, and these vibrations and noises are the members 31, 32, 33, 34 and the fuselage. Vibrates to prevent transmission to the second wall 15.

  In other words, the damping assembly 40 isolates the members 31, 32, 33, 34 connected to the wall 15 from the additional portions 23, 24 connected to the box 14.

  The preload acting on the layer 41 can be adjusted as a function of a predetermined torque acting on the drive shaft 10 and thus a torque reaction acting on the box 14.

  Specifically, the threaded pin 61 is tightened or loosened within the threaded hole 62 to adjust the gripping force acting on the damping assembly 40 in a direction substantially parallel to the respective axis G. This adjusts the preload acting on the layer 41 of elastic material.

  The advantages of the helicopter 1 according to the invention will be clear from the above description.

  In particular, the damping assembly 40 reduces the transmission of vibration and noise within a predetermined frequency range to the wall 15 and the cabin 8 while transmitting torque reaction from the box 14 to the wall 15.

  That is, the elastic material layer 41 is interposed between the cross member 21 fixed to the box 14 and the members 31, 32, 33, 34 fixed to the wall 15 of the body 2, and the load transmitted from the box 14. Vibrated by.

  In other words, the layer 41 of elastic material functions as a mechanical filter that isolates the wall 15 from vibrations and noise in a predetermined frequency range transmitted from the box 14.

  The vibration frequency of the elastic material layer 41 of the coupling device 20 can be adjusted simply by changing the material or shape of the elastic material layer 41, ie adjusting the stiffness.

  Thus, the frequency range for preventing vibrations and noise transmission to the body 2 can be selected at the design stage.

  In other words, the damping assembly 40 can be tuned to various frequency ranges of vibration and noise that reduce transmission to the fuselage 2 at the design stage.

  The adjustment means 60 also allows adjustment of the preload acting on the layer 41 of elastic material of the damping assembly.

  This therefore ensures that the cross member 21 is balanced when the cross member 21 is subjected to a predetermined torque reaction by the box 14 and the elastic action of the layer 41 of elastic material. The predetermined torque reaction exerted by the box 14 is equal to the torque acting on the drive shaft 10 in the normal flight state of the helicopter 1.

  However, it will be apparent that modifications may be made to the helicopter 1 described and illustrated herein without departing from the scope defined by the claims.

DESCRIPTION OF SYMBOLS 1 Helicopter 2 Body 3 Main rotor 7 Transmission 8 Cabin 14 Support main body 15 Wall 21 Cross member (1st connection means, 1st connection member)
22 Flange 23, 24 Additional portion 25, 26 Connecting member (main body)
27 Trapezoidal seat (center seat)
28 Rectangular section seat (side seat)
31, 32 members (second connecting means, a pair of second connecting members)
33, 34 members (second connecting means, another pair of second connecting members)
36 Threaded hole 37 Through hole (second hole)
40 Damping assembly 41 Layer of elastic material (elastic means, first elastic member, second elastic member)
42 Metal plate (first metal member, second metal member)
45 threaded pin 60 adjustment means 61 pin (second threaded pin)
62 Threaded hole (fourth threaded hole)
63 Through-hole (third hole)
B Axis C C Axis D Axis E Axis (longitudinal axis)

Claims (8)

A helicopter (1),
A main rotor (3), a fuselage (2), a transmission (7) operatively coupled to the main rotor (3), a support body (14) supporting at least the transmission (7), and a support body A first connecting means (21) connected to (14), a second connecting means (31, 32, 33, 34) connected to the body (2), and a first connecting means (21); Elastic means (41) interposed between the second connecting means (31, 32, 33, 34),
The first connecting means includes a first connecting member (21), and the first connecting member (21) has a flange (22) connected to the support body (14), And an opening having a first axis (B) across the longitudinal axis (E) of the body (2), the first connecting member (21) further comprising a first additional portion (23) And the second additional portion (24), and the first additional portion (23) and the second additional portion (24) are located on both sides of the first axis (B) and the flange (22). ) Protruding from each part of
The first and second additional portions (23, 24) are V-shaped and include two side portions extending so as to taper on both sides of the first axis (B).
The second connecting means includes a pair of second connecting members (31, 32) disposed on both sides of the first additional portion (23), and both sides of the second additional portion (24). Another pair of second connecting members (33, 34) arranged,
The elastic means (41) includes at least one pair of first members interposed between two side portions of the first additional portion (23) and the pair of second connecting members (31, 32). At least one pair of second members interposed between the elastic member (41), the two side portions of the second additional portion (24) and the other pair of second connecting members (33, 34). A helicopter having the elastic member (41).   The first additional portion (23) and the second additional portion (24) have a second symmetry axis (C) and a third symmetry axis (D), respectively, and the second symmetry axis ( C) and the third axis of symmetry (D) intersect at the center (O) of the opening of the flange (22) and are inclined relative to each other and to the longitudinal axis (E) of the fuselage (2). The helicopter according to claim 1. Furthermore, it has a pair of first damping assemblies (40) and a pair of second damping assemblies (40), each first damping assembly (40) being alternately arranged and integrated. A plurality of first metal members (42) and a plurality of the first elastic members (41),
Each second damping assembly (40) comprises a number of second metal members (42) and a number of said second elastic members (41) arranged alternately and integrated. The helicopter according to 2.   The helicopter according to any one of claims 1 to 3, further comprising an adjusting means (60) for adjusting a preload of the elastic means (41). Further, each of the first additional portion (23) and the second additional portion (24) has one body (25, 26), and each of the main bodies includes the corresponding additional portion ( 23, 24) engaging a central seat (27) and a pair of lateral sides disposed on both sides of the central seat (27) and containing at least a portion of the elastic means (41) A seat (28),
The said main body (25, 26) is connected with the said 2nd connection member (31, 32, 33, 34) corresponding to the said main body in the both sides, The any one of Claims 1-4. Helicopter. The first additional portion (23) and the second additional portion (24) are respectively a first thread extending along the second symmetry axis (C) and the third symmetry axis (D). With a perforated hole (36),
The body (25, 26) extends along the corresponding second symmetry axis (C) and the third symmetry axis (D) and corresponds to the first threaded hole (36). A second hole (37) aligned with
When the first connecting means (21) and the second connecting means (31, 32, 33, 34) are assembled, the first threaded hole (36) and the second hole (37) corresponding to each other. The helicopter according to claim 5, wherein each first threaded pin (45) engages.   The adjusting means (60) includes at least one second threaded pin (61) and the second connecting member (31, 32) for each second connecting member (31, 32, 33, 34). 32, 33, 34) and through which the second threaded pin (61) passes, and at least one third hole (63) formed in the body (25, 26) and the second The helicopter according to claim 5 or 6, comprising at least one fourth threaded hole (62) with which the threaded pin (61) engages.   The fuselage (2) has a cabin (8) and a wall (15) that forms the uppermost part of the cabin (8), and the first connecting member (21) includes the wall (15) The helicopter according to any one of claims 1 to 7, wherein in cooperation, the second connecting member (31, 32, 33, 34) is fixed to the wall (15).